US10625873B2 - System for controlling a controlled parameter - Google Patents

System for controlling a controlled parameter Download PDF

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US10625873B2
US10625873B2 US15/752,628 US201615752628A US10625873B2 US 10625873 B2 US10625873 B2 US 10625873B2 US 201615752628 A US201615752628 A US 201615752628A US 10625873 B2 US10625873 B2 US 10625873B2
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command
operating law
model
operating
regulated parameter
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US20190031359A1 (en
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Cedrik Djelassi
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Safran Aircraft Engines SAS
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Safran Aircraft Engines SAS
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    • G—PHYSICS
    • G05—CONTROLLING; REGULATING
    • G05B—CONTROL OR REGULATING SYSTEMS IN GENERAL; FUNCTIONAL ELEMENTS OF SUCH SYSTEMS; MONITORING OR TESTING ARRANGEMENTS FOR SUCH SYSTEMS OR ELEMENTS
    • G05B13/00—Adaptive control systems, i.e. systems automatically adjusting themselves to have a performance which is optimum according to some preassigned criterion
    • G05B13/02—Adaptive control systems, i.e. systems automatically adjusting themselves to have a performance which is optimum according to some preassigned criterion electric
    • G05B13/04—Adaptive control systems, i.e. systems automatically adjusting themselves to have a performance which is optimum according to some preassigned criterion electric involving the use of models or simulators
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D31/00—Power plant control systems; Arrangement of power plant control systems in aircraft
    • B64D31/02—Initiating means
    • B64D31/06—Initiating means actuated automatically
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C9/00—Controlling gas-turbine plants; Controlling fuel supply in air- breathing jet-propulsion plants
    • G—PHYSICS
    • G05—CONTROLLING; REGULATING
    • G05B—CONTROL OR REGULATING SYSTEMS IN GENERAL; FUNCTIONAL ELEMENTS OF SUCH SYSTEMS; MONITORING OR TESTING ARRANGEMENTS FOR SUCH SYSTEMS OR ELEMENTS
    • G05B13/00—Adaptive control systems, i.e. systems automatically adjusting themselves to have a performance which is optimum according to some preassigned criterion
    • G05B13/02—Adaptive control systems, i.e. systems automatically adjusting themselves to have a performance which is optimum according to some preassigned criterion electric
    • G05B13/04—Adaptive control systems, i.e. systems automatically adjusting themselves to have a performance which is optimum according to some preassigned criterion electric involving the use of models or simulators
    • G05B13/042—Adaptive control systems, i.e. systems automatically adjusting themselves to have a performance which is optimum according to some preassigned criterion electric involving the use of models or simulators in which a parameter or coefficient is automatically adjusted to optimise the performance
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C6/00—Plural gas-turbine plants; Combinations of gas-turbine plants with other apparatus; Adaptations of gas-turbine plants for special use
    • F02C6/20—Adaptations of gas-turbine plants for driving vehicles
    • F02C6/206—Adaptations of gas-turbine plants for driving vehicles the vehicles being airscrew driven
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2220/00—Application
    • F05D2220/30—Application in turbines
    • F05D2220/32—Application in turbines in gas turbines
    • F05D2220/323—Application in turbines in gas turbines for aircraft propulsion, e.g. jet engines
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2270/00—Control
    • F05D2270/01—Purpose of the control system
    • F05D2270/02—Purpose of the control system to control rotational speed (n)
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2270/00—Control
    • F05D2270/30—Control parameters, e.g. input parameters
    • F05D2270/335—Output power or torque
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2270/00—Control
    • F05D2270/40—Type of control system
    • F05D2270/44—Type of control system active, predictive, or anticipative
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2270/00—Control
    • F05D2270/70—Type of control algorithm
    • F05D2270/71—Type of control algorithm synthesized, i.e. parameter computed by a mathematical model

Definitions

  • the field of the present invention is that of systems for controlling a regulated parameter of an aeronautical equipment device and applies advantageously to an aircraft propulsion device.
  • Operating a device equipping an aircraft, such as an engine, is highly complex, involving many parameters, and restrictions on security specific to aeronautics need particularly precise and secure control.
  • the invention applies advantageously to turboprops and more particularly to determination of a command for servo-controlling the power of such a turboprop and to servo-control the speed of its propeller.
  • FIG. 1 illustrates a regulation control system 1 by servo-control at a setpoint Y c of a regulated parameter Y of a physical device 2 .
  • the control aims at maintaining at least one physical magnitude, called regulated parameter, equal to a targeted value, called setpoint, by action on a regulating variable by means of a command U.
  • the system 1 comprises a regulator 3 delivering said command U and inputting the output ⁇ of a differentiator 5 delivering the difference between a loop back 4 of the regulated parameter Y and the setpoint Y c .
  • Such a system is currently being used in automation for servo-controlling the regulated parameter Y at the setpoint Y c .
  • the difficulty is determining the transfer function of the regulator 3 . In fact, it is this transfer function which determines the behavior of the device 2 , via the command U.
  • it is easy to determine the form of the transfer function of the regulator 3 to achieve a response from the device 2 which satisfies the requisites for rapidity and security. But as long as the device gets complex, designing an acceptable regulator 3 becomes complicated, or even impossible.
  • the aim of the present invention is to rectify the disadvantages of the prior art by proposing a system for controlling a regulated parameter of an aeronautical equipment device, said regulated parameter being governed by an operating law linking said regulated parameter to a command and to a plurality of input parameters, said regulation control system comprising a regulation loop servo-controlling said regulated parameter at a setpoint b means of the command controlling the device,
  • the system comprises a compensation module of the operating law and a determination module of a local gain configured to determine the local gain of a static part of a model of the operating law representative of the gain of said regulated parameter in response to a variation in said command in a steady operating state of said operating law, said static part of the model of the operating law combining the time-independent relations between the regulated parameter, the command and the plurality of input parameters, said model of the operating law also comprising a dynamic part combining the time-dependent relations between the regulated parameter, the command and the plurality of input parameters, said compensation module of the operating law involving the inverse of said local gain.
  • a compensation module of the operating law of the inverse of a local gain thus determined in this way compensates the operating law even in the event of non-linearities in the operating law.
  • the regulated parameter can be servo-controlled by dispensing with these non-linearities.
  • the invention also relates to an assembly comprising an aeronautical equipment device and a system for controlling said device according to the invention.
  • FIG. 1 is a drawing illustrating a regulation control system by servo-control at a setpoint of a regulated parameter of a physical device
  • FIGS. 2, 3 and 4 are drawings illustrating, a regulation control system by servo-control at a setpoint of a regulated parameter of a physical device according to possible embodiments of the invention
  • FIGS. 5 to 9 are drawings illustrating an exemplary embodiment of the invention.
  • module means a set of technical means carried out to satisfy the function of the module. Typically, these are equations and calculations whereof the functions are linked and can be combined.
  • the present invention is carried out by a computer and its accessories (memory, input/outputs) which constitute the structural part of the regulation control system.
  • transfer function or model could be used interchangeably to designate a model, though the term model implies the need to consider an operating law of a physical system modelled by said model.
  • FIG. 2 shows the principle of a system 1 according to the invention.
  • this is a regulation control system 1 by servo-control at a setpoint Y c of a regulated parameter Y of a physical device 2 .
  • the system 1 comprises a regulation loop servo-controlling the regulated parameter Y at a setpoint Y c by controlling the device 2 by the command U.
  • This regulation loop comprises a regulator 3 delivering the command U and inputting the output of a differentiator 5 delivering the difference between a loop back 4 of the regulated parameter Y and the setpoint Y c .
  • the regulated parameter Y is governed by an operating law linking said regulated parameter Y to a command U and to a plurality of input parameters X 1 , X 2 , X 3 . . . .
  • This operating law can be modelled by a transfer function F(p), mathematical model of the relationship between the command U, the input parameters X i and the regulated parameter Y.
  • the regulator 3 is constructed from two modules in series: a corrector 6 with a transfer function C(p) and a compensation module 7 of the operating law with a transfer function F 1 (p).
  • the corrector 6 and the compensation module 7 are preferably in series in the forward path of the regulation loop, with the corrector 6 upstream of the compensation module 7 .
  • the command U corresponds to the output of the regulator 3 , and therefore to the output of the corrector 6 or of the compensation module 7 .
  • Y the parameter to be regulated, i.e., the output delivered by the model of the operating law, U the command, and X 1 , X 2 , X 3 . . . being input parameters which influence the operating law.
  • the model of the operating law can be determined by the physical relationships between different known variables, i.e., by analysis, and/or by identification.
  • the transfer function F(p) is determined from this model to reflect its operation.
  • the model f of the operating law comprises two parts: a static part and a dynamic part.
  • the static part of the model of the operating law combines the time-independent relationships between the regulated parameter Y, the command U and the plurality of input parameters X i .
  • the dynamic part of the model of the operating law combines the time-dependent relationships between the regulated parameter Y the command U and the plurality of input parameters X i .
  • Y K ( U,X 1 ,X 2 ,X 3 , . . . ) ⁇ f ′( U,X 1 ,X 2 ,X 3 , . . . )
  • K(U, X 1 , X 2 , X 3 , . . . ) represents the static part, representative of the operating law in steady state, i.e., when the command U and the plurality of input parameters X i are constant in the time for sufficiently long so that the effects of the transitory phases are negligible.
  • Y K ( U,X 1 ,X 2 ,X 3 , . . . )
  • the elements of the static part are determined either by identification in steady state or by analyze.
  • f′(U, X 1 , X 2 , X 3 , . . . ) represents the dynamic part, representative of the effects on the operating law of temporal variations of the command U and/or of the plurality of input parameters X i .
  • f ′( U,X 1 ,X 2 ,X 3 , . . . ) 1
  • This dynamic part f′(p) can be written as a transfer function of unitary static gain:
  • the elements of the dynamic part are determined either by identification in transitory state or by analysis.
  • Inversion of the transfer function of the model of the operating law poses no problem for what is its dynamic part:
  • the solution is to calculate a local gain of the static part of a model of the operating law representative of the gain ⁇ Y of the regulated parameter Y in response to a variation ⁇ U of the command U in a steady operating state of said operating law:
  • This calculation is performed by a determination module of the local gain, in the core of the computer charged with control of the regulated parameter Y.
  • the determination module of the local gain is configured so that at least with each change of the command U and/or the input parameters X i , a new local gain is deter mined to reflect said changes. Specifically, the local gain is calculated in real time at each time step of calculation of the regulation control to update said local gain.
  • FIG. 3 shows the arrangement of this determination module of the local gain 8 in a system similar to that of FIG. 2 .
  • the determination module of the local gain 8 receives at input the input parameters X i , i.e., X 1 , X 2 , X 3 , and the command U, and delivers the local gain to the compensation module 7 of the regulator 3 .
  • the determination module of the local gain 8 calculates the local gain from the values taken by the outputs of the static part of a model of the operating law for at least two separate values of the command U in keeping the input parameters constant:
  • the two separate values of the command are separated in value by a difference ⁇ U.
  • This difference ⁇ U is selected sufficiently small to remain in the linear field of the static part of the transfer function of the model of the operating law, i.e., it is possible to disregard any non-linearities around the current operating point of the system.
  • the difference ⁇ U between the two separate values of the command U is preferably less than 0.25% of the range of variation in said command U andlor the difference ⁇ U between the two separate values of the command U corresponds to a variation in said command U causing a variation ⁇ Y in the regulated parameter Y less than 1% of the range of variation in said regulated parameter Y.
  • the module 7 involves the inverse of the local gain.
  • the inverse of the transfer function of the model of the operating law can be written as:
  • the transfer function C(p) of the corrector 6 can therefore be developed without any consideration for non-linearities of the operating law of the device 2 to ensure that the closed-loop transfer function responds to the need for planned control.
  • the transfer function C(p) of the corrector 6 can be selected for example to admit integration in the regulation loop and thereby ensure deletion of the permanent error on the regulated parameter Y for the setpoint Yc of step type. In this case the choice of gain in, the transfer function C(p) of the corrector 6 controls the closed-loop response to satisfy the requisites of response times, independently of the behavior of the device since its operating law is compensated.
  • Some transfer functions of the model of the operating law can have particular features to be considered. This is especially the case when the device 2 has hysteresis. This is the case for example of pneumatic valves.
  • the regulated parameter Y reacts only after the command has travelled the hysteresis. From the viewpoint of the corrector 3 , this corresponds to a local gain which tends to 0, i.e., in the interval of hysteresis the variation in the command U produces no evolution of the regulated parameter Y. In other words, in the interval of hysteresis, the command U has no effect on the output, i.e. the regulated parameter Y, provided the command U is not outside of the hysteresis.
  • the local gain is therefore zero.
  • the local gain being reversed to compensate the gain of the operating law of the device 2 , the gain of the compensation module tends to the infinite, corresponding to an infinitely large command U. It can therefore be ensured that the determination module of the local gain is configured to deliver a predetermined saturation value when the local gain calculated by said determination module is below a predefined value, in absolute value.
  • This saturation value avoids a software exception which would cause division by zero during inversion of the local gain.
  • this saturation value is selected, typically very small, such that once reversed it maximizes the command generated by the regulator 3 . This generates a rapid command which allows the course of the interval of hysteresis in a short period. Performance of the control is thereby improved despite the presence of hysteresis.
  • Another particular feature which can be factored in is for example the presence of a non-invertible part in the transfer function of the model of the operating law. This is for example the case for a pure delay. This non-invertible pan cannot be compensated, but its inclusion in the compensation module 7 of the operating law compensates the invertible part of the model of the operating law.
  • this shows an example of inclusion of this non-invertible part in the compensation module 7 .
  • the compensation module 7 of the operating law comprises first a static compensation 70 which corresponds to the inverse of the local gain K then a dynamic compensation, downstream of the static compensation 70 , comprising a forward path 72 and a feedback path 71 constituting a feedback loop.
  • the forward path 72 comprises a transfer function involving the inverse of the invertible part of the model of the operating law. This reverse compensates the invertible part of the model of the operating law.
  • the transfer function of the forward path 72 also comprises a transfer function F′ 1 (p) corresponding to the dynamics desired for the transfer function in closed loop. In this way, the transfer function of the forward path 72 corresponds to:
  • the feedback path 71 comprises the transfer function F 2 (p) involving the non-invertible part of the model of the operating law.
  • the feedback path 71 also comprises the transfer function F 1 (p) corresponding to the invertible part of the model of the operating law. In this way, the transfer function of the feedback path 71 corresponds to F 2 (p) ⁇ F 1 (p).
  • the output of this feedback path 71 is summed at the output of the static compensation 70 to form the input of the forward path 72 , whereof the output is the command U and is also the input of the feedback path 71 .
  • the corrector 6 therefore imposes the desired dynamics on the whole without static error, and the perturbation can be efficaciously rejected by selecting a rapid dynamic for F′ 1 (p).
  • the system is of particular interest when the non-invertible part is sufficiently modellable. This is the case for a pure delay.
  • the delay does not affect the stability of the CLTF. However, rejection of the perturbation is affected by the delay. However, in case of significant delay it is interesting to select the corrector 6 so as to improve the efficacy of rejection.
  • the following non-limiting example is given in the event where the device is a turboprop, and the regulated parameter is the rotational speed of the propeller XNP, the command being the pitch of the propeller ⁇ .
  • the command ⁇ is identified by Beta in FIGS. 6 to 9 .
  • the example illustrates the application of the invention for calculation of F ⁇ 1 (p) in reference to FIG. 3 , which corresponds to a possible embodiment of the invention.
  • TRQ 49 - TRQ P GR ( J L + J P GR 2 ) ⁇ d ⁇ ⁇ ⁇ L dt
  • TRQ 49 - TRQ P GR ( J L + J P GR 2 ) ⁇ GR ⁇ d ⁇ ⁇ ⁇ p dt
  • the aim is to disclose the power term:
  • K ⁇ ⁇ 2 10 - 3 * ⁇ * ( DIA ⁇ ⁇ 91 60 ) 3 * A ⁇ ⁇ 91
  • a ⁇ ⁇ 91 ⁇ 4 * DIA ⁇ ⁇ 91 2 * ( 1 - XNU ⁇ ⁇ 91 2 )
  • RJ91 the airspeed coefficient (see table 1).
  • a model of the evolution of the speed of the propeller of a turboprop shown in FIG. 5 is achieved, in which the block 50 correspond to calculation of the product of the constant K2 by the propeller power coefficient RCP91. This product is multiplied by the rotational speed of the propeller ⁇ P (OmegaP) previously calculated, and cubed.
  • a loop back 51 illustrates the inclusion of the rotational speed of the propeller by the block 50 and by the cubic function.
  • the power absorbed by the propeller Pw p is achieved as a function of the command ⁇ , of the measurement of the rotational speed of the propeller, via the loop back 51 , and input parameters comprising the advancement speed of the aircraft VTAS, the ambient pressure PAMB and the ambient temperature TAMB.
  • This power absorbed by the propeller Pw p is subtracted from another input parameter constituted by the power delivered by the power turbine Pw 49 .
  • the units are to be converted by certain magnitudes. In this way, the kilowatts of Pw p and Pw 49 are converted to watts.
  • the result is divided by the speed ⁇ P , then by the total inertia J_ Tot .
  • This result is then integrated by initializing with an initial speed XNP Init , converted previously from rpm in rad/s. The result after integration is the speed XNP, reconverted from rad/s in rpm.
  • This transfer function is simplified so as to reveal a low-pass system of order 1 , representative of the dynamic of the propeller, whereof the time constant Tau_propeller is variable as a function of inputs, and therefore the gain corresponds to the steady part of the rotational speed XNP_Stab:
  • XNP XNP_Stab ⁇ 1 1 + Tau_propeller ⁇ P
  • FIG. 6 illustrates this modified transfer function. Relative to FIG. 5 , the disappearance of the inclusion of the rotational speed of the propeller is noted on output from the block 50 , via the loop back 51 and the cubic function. Instead, the product of the constant K2 by the propeller power coefficient RCP91 corresponds to the power absorbed by the propeller P wp which divides the power delivered by the power turbine Pw 49 , and a cubic root function is applied to the result to give the steady part of the rotational speed XNP_Stab.
  • the measurement of the rotational speed XNP is subtracted from the steady part of the rotational speed XNP_Stab via a loop back 52 .
  • the result is divided by Tau_propeller, then integrated by initializing with an initial speed XNP Init selected at zero, to give the measurement of the rotational speed XNP measurement in rpm.
  • the transformation of the transfer function isolates the stabilized relationship between the inputs and the rotational speed in steady XNP_Stab, from the transitory relationship.
  • the steady relationship is calculated directly from the model transformed in this way, but the analytical expression of the time constant of the first order low-pass system is not possible.
  • the time constant Tau_propeller is approximated as being a function of PW49 by identifying the dynamics of XNP by conventional identification methods such as application of a level of power input and by measuring. This approximation is sufficiently faithful to enable the synthesis of F ⁇ 1 (p) for control of the propeller.
  • FIG. 7 illustrates implementation of the calculation of the local gain such as can be done in a real-time computer. This therefore relates to the determination module 8 of the local gain.
  • the two blocks 81 , 82 in parallel input the measurement of the rotational speed of the propeller ⁇ P (OmegaP) the advancement speed of the aircraft VTAS, the ambient pressure PAMB, the ambient temperature TAMB, and the power delivered by the power turbine Pw 49 .
  • the block 81 from above, noted Static Model XNP1 takes ⁇ as command while the block 82 from below, noted Static Model XNP2, takes ⁇ + ⁇ as command, and therefore deliver two values of XNP, noted XNP1 and XNP2.
  • These are therefore blocks illustrating the static model of the operating law. After having made the difference between XNP1 and XNP2, and after division by ⁇ , the result is the value of the local gain, noted local gain XNP vs Beta.
  • FIG. 8 illustrates the static part of the model of the operating law schematized by the blocks 81 , 82 in FIG. 7 , in this case that of the block 81 from above, disclosing the block 50 shown in FIG. 5 .
  • This is in fact the static part of the transfer function illustrated by FIG. 6 : the dynamic part involving the Tau_Propeller and the integrator has been deleted.
  • Introduction of a delay 80 of a calculation pitch on the loop back 51 of the measurement of the XNP is also noted, so that measuring the preceding calculation pitch is considered by replacement of the integration.
  • Complete compensation of the model of the operating law linking XNP to ⁇ is finally made by reversing the local gain and the low-pass filter of order 1 corresponding to the dynamic of the system, as illustrated in FIG. 9 .
  • This shows the determination module 8 of the local gain K illustrated by FIG. 7 , and the compensation module 7 of the operating law, via the high-pass filter 73 constituting the inverse of the dynamic part (identified at a low-pass) divided by the local gain K determined by the module 8 .
  • ⁇ is the difference between a setpoint of rotational speed XNP and measurement of the rotational speed XNP.
  • the difference is made between the current ⁇ and ⁇ previously calculated, symbolized by the delay. This difference is divided by Ts, representing a part of the time constant. The result is multiplied by Tau_Propeller, then added to ⁇ . The output of the high-pass filter 73 is divided by the local gain K calculated by the module 8 , resulting in the command ⁇ to be applied.

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Applications Claiming Priority (3)

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FR1557808 2015-08-19
FR1557808A FR3040220B1 (fr) 2015-08-19 2015-08-19 Systeme de regulation d'un parametre regule
PCT/FR2016/052090 WO2017029456A1 (fr) 2015-08-19 2016-08-18 Système de régulation d'un paramètre régulé

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CN (1) CN107924163B (zh)
BR (1) BR112018003049B1 (zh)
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FR3070056B1 (fr) * 2017-08-09 2019-08-23 Safran Aircraft Engines Systeme mixte de commande de moteur d'aeronef et procede de reglage associe
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